微型飞行器低雷诺数流场显示试验研究

在南航非定常风洞内,对一盘状微型飞行器的气动特性进行了测力和流场显示实验,给出了不同迎角下微型飞行器的空间流场显示结果.研究表明:随着迎角的增加,在机翼上表面开始形成前缘分离涡,并且前缘涡的尺度和强度不断增加.迎角继续增大,前缘涡首先在后缘开始破裂,并不断前移,最终导致微型飞行器的失速.模型上前缘分离涡的形成、发展和破裂是导致盘状微型飞行器气动力特性产生变化的根本原因.

Flow visualization experiments of MAV in low Reynolds number

The aerodynamic characteristics and flow field visualizations of a MAV are investigated in NUAA unsteady wind tunnel.The results show that the leading-edge vortex form at low angles of attack first.The scales of the vortex are enlarged and the strength is enhanced with the angle of attack increasing.But the leading-edge vortex breaks down at the trailing-edge quickly.when angle of attack continually increasing,the position of vortex breakdown moves upstream.Finally the MAV stalls when the leadingedge vortex breaks down at the whole upper surface.The appearance,development and breakdown of the leading edge vortex are the important factors for the aerodynamic characteristics of this MAV.